CN116906184A - Cascade type radial adjustable pre-rotation system of aero-engine air system - Google Patents
Cascade type radial adjustable pre-rotation system of aero-engine air system Download PDFInfo
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- CN116906184A CN116906184A CN202310928076.XA CN202310928076A CN116906184A CN 116906184 A CN116906184 A CN 116906184A CN 202310928076 A CN202310928076 A CN 202310928076A CN 116906184 A CN116906184 A CN 116906184A
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- 238000007789 sealing Methods 0.000 claims abstract description 94
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Abstract
The invention relates to a cascade type radial adjustable pre-rotation system of an aero-engine air system, belongs to the technical field of aero-engines, and solves the problems that in the prior art, the excessive air-entraining amount is easy to cause the reduction of engine thrust and the increase of fuel consumption, the waste of cooling air by constant-proportion air-entraining and the insufficient stability of the air system endanger the safety of the engine. According to the invention, the throttle area can be changed by adjusting the deflection angle of the guide vane of the adjustable pre-rotation nozzle, the adjustment of the air-entraining amount of cooling air is realized, the hot end component of the engine is ensured to meet the allowable temperature requirement, cooling air is saved as much as possible, and the performance and the safety of the engine are considered; the air inlet angle is basically unchanged in the adjusting process, the air flow direction is relatively fixed during adjusting, and the air inlet loss is small; radial pre-rotation is adopted, so that leakage is reduced, waste of pre-rotation gas is avoided, and stability of an air system is improved; the sealing comb teeth on two sides of the pre-rotation cavity improve the stability of the air system.
Description
Technical Field
The invention relates to the technical field of aeroengines, in particular to a cascade type radial adjustable pre-rotation system of an aeroengine air system.
Background
The pre-rotation system of the aircraft engine air system is used to provide cooling air of suitable pressure and flow rate to the turbine blades.
Because the air-entraining amount of the modern aeroengine air system exceeds 25%, and the air in the air system does not participate in circulation work, the excessive air-entraining amount is easy to cause the reduction of engine thrust and the increase of fuel consumption, and the engine performance and the aircraft performance are adversely affected. In addition, the constant-proportion air-entraining mode adopted by the aero-engine air system can cause waste of cooling air in a state of low temperature in front of the turbine, and is not beneficial to improvement of engine performance. Meanwhile, transient effect enhancement in the transition process of the advanced aeroengine in the future and adjustment of the angle of the turbine guide vane can lead to the obvious enhancement of pressure fluctuation of the air film hole of the turbine blade, and the occurrence of engine safety hazard such as backflow of the gas generated by the air film Kong Yifa of the turbine blade. Most of the pre-spinning systems of the prior aero-engines adopt an axial air inlet high-position pre-spinning design, and the purpose of the pre-spinning system is to increase the pre-spinning temperature drop by using a higher tangential speed. However, as the Mach number at the inlet of the aeroengine and the temperature before the turbine are improved, the deformation of the rotor and the stator is increased, and the high-position comb tooth space changes to cause the flow and the pressure of the front cavity and the rear cavity to fluctuate in a large range, so that the stable realization of main functions of axial force control, rim sealing and the like of an air system of the aeroengine is affected.
In summary, the problems that the engine thrust is reduced, the fuel consumption is increased, the constant proportion bleed air wastes cooling gas and the stability of the air system is insufficient and the safety of the engine is endangered due to the fact that the bleed air amount of the air system of the aeroengine is excessive in the prior art.
Disclosure of Invention
In view of the problems, the invention provides a vane grid type radial adjustable pre-rotation system of an aero-engine air system, which solves the problems that in the prior art, the air entraining amount of the aero-engine air system is excessive, the thrust of the engine is easy to be reduced, the fuel consumption is increased, the cooling gas is wasted by constant-proportion air entraining, and the stability of the air system is insufficient to endanger the safety of the engine.
The invention provides a cascade type radial adjustable pre-rotation system of an aero-engine air system, which comprises an adjustable pre-rotation nozzle 101, a cascade type pre-rotation channel 102 and a driving mechanism; wherein,,
the adjustable pre-rotation nozzles 101 are uniformly arranged in the blade-grid-type pre-rotation channel 102 along the circumferential direction, and the direction of the adjustable pre-rotation nozzles 101 is radial and is used for pre-rotating cooling two air flows entering the combustion chamber of the blade-grid-type pre-rotation channel 102;
the adjustable pre-rotation nozzle 101 comprises an adjustable pre-rotation nozzle guide vane 101a and a guide plate 101b, the adjustable pre-rotation nozzle guide vane 101a can deflect at an angle relative to the guide plate 101b, the cross section area of the adjustable pre-rotation nozzle 101 in the radial cross section of the cascade pre-rotation channel 102 is changed, the radial cross section area of the cascade pre-rotation channel 102 is further increased or reduced, and the gas flow passing through the cascade pre-rotation channel 102 is adjusted;
the drive mechanism is driven by an aircraft engine hydraulic system for driving the deflection of the adjustable pre-rotation nozzle guide vanes 101a relative to the deflector 101 b.
Further, the vane back curve of the adjustable pre-rotation nozzle guide vane 101a and the tail curve of the guide plate 101b are in smooth transition; the leading edge curve of the deflector 101b is parallel to the leading edge curve of the adjustable pre-rotation nozzle vane 101 a.
Further, the maximum deflection angle of the adjustable pre-rotation nozzle guide vane 101a relative to the deflector 101b corresponds to a sub-inspection state of the adjustable pre-rotation nozzle guide vane 101a, in which the adjustable pre-rotation nozzle guide vane 101a is partially overlapped with the deflector 101b, the cross-sectional area of the adjustable pre-rotation nozzle 101 under the radial cross-section of the cascade pre-rotation channel 102 is maximum, and the gas flow through the cascade pre-rotation channel 102 is minimum; the minimum deflection angle of the adjustable pre-rotation nozzle guide vane 101a relative to the deflector 101b corresponds to the maximum state of the adjustable pre-rotation nozzle guide vane 101a, in which the adjustable pre-rotation nozzle guide vane 101a is fully overlapped with the deflector 101b, the cross-sectional area of the adjustable pre-rotation nozzle 101 at the radial cross-section of the cascade type pre-rotation channel 102 is minimum, and the gas flow through the cascade type pre-rotation channel 102 is maximum.
Further, the cascade radially adjustable pre-rotation system of the aero-engine air system further comprises a combustion chamber outer ring 105 and a pre-rotation channel support plate; the upper part of the combustion chamber outer ring 105 extends downwards to form a pre-rotation channel support plate, and the pre-rotation channel support plate and the combustion chamber outer ring 105 are fixed on an engine stator supporting structure; the pre-rotation channel struts surround to form a cascade of pre-rotation channels 102.
Further, the driving mechanisms are uniformly arranged on the outer side of the pre-rotation channel support plate along the circumferential direction, and comprise a hydraulic actuating mechanism 112, an actuating rod 113, a connecting rod 114, a transmission ring 115, a transmission rod 116 and a pin 119;
one end of the hydraulic actuating mechanism 112 is fixed on the upper part of the combustion chamber outer ring 105 and is driven by an aero-engine hydraulic system; the other end of the hydraulic actuating mechanism 112 is connected with an actuating rod 113, and the actuating rod 113 can stretch and retract in the radial direction under the drive of the hydraulic actuating mechanism 112 so as to drive a connecting rod 114 to move; one end of the connecting rod 114 is connected with the actuating rod 113, and the other end is connected with the actuating ring 115; the actuating ring 115 is a thin-walled ring capable of rotating circumferentially under the action of the connecting rod 114; the actuating ring 115 is connected with the transmission rod 116 through a pin 119, drives the transmission rod 116 and the adjustable pre-rotation nozzle guide vane 101a connected with the transmission rod to rotate, and drives the adjustable pre-rotation nozzle guide vane 101a to deflect relative to the guide plate 101 b.
Further, the cascade radially adjustable pre-rotation system of the aero-engine air system further comprises a pre-rotation chamber 103 for collecting pre-rotated cooling gas passing through the cascade pre-rotation channel 102.
Further, the cascade type radial adjustable pre-rotation system of the aero-engine air system further comprises a cover plate 104, and an outer sealing grate tooth 104b and an inner sealing grate tooth 104c are arranged on the cover plate 104; an outer grate teeth sealing ring 105b and an inner grate teeth sealing ring 105c are arranged at the lower part of the combustion chamber outer ring 105; the outer sealing comb teeth 104b, the inner sealing comb teeth 104c, the outer comb teeth sealing ring 105b, the inner comb teeth sealing ring 105c and the cover plate 104 jointly enclose to form the pre-rotation cavity 103.
Further, the cascade type radially adjustable pre-rotation system of the aero-engine air system further comprises an unloading cavity 108; the outer sealing comb teeth 104b and the outer comb teeth sealing ring 105b act together to seal the pre-rotation cavity 103 from the unloading cavity 108 by the pre-rotation cooling gas.
Further, the cascade radially adjustable pre-rotation system of the aero-engine air system further comprises a disc front seal cavity 107; the inner sealing comb teeth 104c and the inner comb teeth sealing ring 105c act together to seal the pre-spun cooling air in the pre-spinning cavity 103 from the front disc sealing cavity 107.
Further, a gap exists between the outer sealing comb teeth 104b and the outer comb teeth sealing ring 105 b; a gap exists between the inner sealing comb teeth 104c and the inner comb teeth sealing ring 105 c.
Compared with the prior art, the invention has at least the following beneficial effects:
(1) According to the vane grid type radial adjustable pre-rotation system of the aero-engine air system, disclosed by the invention, the throttle area of the adjustable pre-rotation nozzle guide vane can be changed by adjusting the deflection angle of the adjustable pre-rotation nozzle guide vane, the adjustment of the air-entraining amount of pre-rotation cooling air is realized, the hot end part of the engine is ensured to meet the allowable temperature requirement by using cooling air with proper flow, meanwhile, the cooling air is saved as much as possible, the performance of the engine is ensured, and meanwhile, the events of endangering the engine, such as backflow of gas generated by the turbine blade air film Kong Yifa, are effectively avoided.
(2) According to the vane grid type radial adjustable pre-rotation system of the aeroengine disclosed by the invention, the vane back curve of the adjustable pre-rotation nozzle vane is in smooth transition with the tail curve of the guide plate under the maximum state, the head curve of the guide plate and the front curve of the adjustable pre-rotation nozzle vane are concentric circles, so that the air inlet angle is basically unchanged in the process of adjusting the deflection angle of the adjustable pre-rotation nozzle vane, the air inlet loss in the adjusting process is reduced, the air flow direction is relatively fixed when the angle adjustment is carried out on the pre-rotation nozzle through the combination of the guide plate and the adjustable pre-rotation nozzle vane, the flow loss in the cooling air flow adjusting process is reduced, and the high-efficiency and stable adjustment of the cooling air flow is realized.
(3) The invention discloses a vane grid type radial adjustable pre-rotation system of an aero-engine air system, which drives a connecting rod through a hydraulic actuating mechanism so as to drive a transmission ring to rotate. The transmission rod connected with the guide vane of the adjustable pre-rotation nozzle is connected with the transmission ring through a pin, and the transmission ring drives the guide vane of the adjustable pre-rotation nozzle to rotate, so that the deflection angle of the guide vane of the adjustable pre-rotation nozzle is adjusted.
(4) According to the vane grid type radial adjustable pre-rotation system of the aeroengine air system, as radial pre-rotation is adopted, the radius of an outlet of an adjustable pre-rotation nozzle is reduced, the radius of sealing comb teeth positioned at two sides of the outlet of the adjustable pre-rotation nozzle is reduced, and smaller sealing gaps can be adopted for the low-radius comb teeth, so that the leakage amount is reduced, the waste of pre-rotation air is avoided, meanwhile, the influence of deformation of a rotor on the low-position comb teeth is small, and the stability of the air system is improved.
(5) According to the vane grid type radial adjustable pre-rotation system of the aero-engine air system, due to the existence of the sealing comb teeth at the two sides of the pre-rotation cavity, the pressure change of the pre-rotation cavity, the disc front cavity and the unloading cavity is relatively independent, the influence of the pressure change of the pre-rotation cavity on the axial force during the angle adjustment of the adjustable pre-rotation nozzle is avoided, and the stability of the air system is further improved.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention.
FIG. 1 is a schematic view of a cascade type radially adjustable pre-rotation system of an aero-engine air system of the present disclosure;
FIG. 2 is a schematic view of a partially enlarged structure of a plurality of groups of adjustable pre-rotation nozzle vanes, deflectors, and fixed spindles disclosed herein;
FIG. 3 is a schematic diagram of an adjustable pre-rotation nozzle drive mechanism according to the present disclosure;
FIG. 4 is a schematic diagram of a decoupling design of a rim seal flow path and a cooling flow path according to the present disclosure; .
FIG. 5 is a schematic illustration of an adjustable pre-rotation nozzle vane adjustment of the present disclosure;
FIG. 6 is a schematic diagram of a conventional cover plate type pre-rotation system;
FIG. 7 is a graph comparing bleed air ratios of a cascade radially adjustable pre-rotation system of an aircraft engine air system of the present disclosure with a conventional cover plate pre-rotation system in different flight conditions;
fig. 8 is a graph comparing flow stability of a seal flow path of a cascade type radial adjustable pre-rotation system and a conventional cover plate type pre-rotation system of an air system of an aeroengine.
Reference numerals:
101-an adjustable pre-rotation nozzle; 101 a-adjustable pre-rotation nozzle vanes; 101 b-a deflector; 102-cascade pre-rotation channels; 103-pre-rotation cavity; 104-cover plate; 104 a-receiving aperture; 104 b-sealing the grate teeth; 104 c-sealing the grate teeth; 105-a combustion chamber outer ring; 105 a-vent holes; 105 b-an outer grate sealing ring; 105 c-inner grate teeth sealing ring; 105 d-orifice; 105 e-pre-rotation channel outer support plate; 105 f-pre-screwing the inner support plate of the channel; 106-an air collection cavity; 107-sealing the cavity in front of the disk; 108-unloading cavity; 109-drum shaft; 110-turbine disk; 110 a-a gas supply hole; 111-cover plate cavity; 112-hydraulic actuation mechanism; 113-an actuating lever; 114-a connecting rod; 115-a drive ring; 116-transmission rod; 117-fixed spindle; 118-supporting plates; 119-pin; 120-external sealing of a traditional cover plate type pre-rotation system; 121-a pre-rotation nozzle of a conventional cover plate pre-rotation system; 122-inner seal of the existing traditional cover plate type pre-rotation system; 123-air supply holes of conventional cover plate pre-rotation systems; 124-a cover plate cavity of a conventional cover plate type pre-rotation system; 125-receiving holes of conventional cap plate-type pre-rotation systems; 126-cover plate of conventional cover plate pre-rotation system; 127-pre-spin chamber of a conventional cover plate pre-spin system.
Detailed Description
In order that the above-recited objects, features and advantages of the present invention will be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description. It should be noted that, without conflict, the embodiments of the present invention and features in the embodiments may be combined with each other. In addition, the invention may be practiced otherwise than as specifically described and thus the scope of the invention is not limited by the specific embodiments disclosed herein.
In one embodiment of the invention, as shown in fig. 1, a cascade type radial adjustable pre-rotation system of an aeroengine air system is disclosed, comprising an adjustable pre-rotation nozzle 101, a cascade type pre-rotation channel 102, a pre-rotation cavity 103, a cover plate 104, a combustion chamber outer ring 105, a pre-rotation channel support plate, an air collection cavity 106, a disc front sealing cavity 107, an unloading cavity 108, a drum shaft 109, a turbine disc 110, a cover plate cavity 111, a driving mechanism, a fixed rotating shaft 117 and a support plate 118; the driving mechanism includes a hydraulic actuating mechanism 112, an actuating lever 113, a connecting rod 114, a transmission ring 115, a transmission rod 116, and a pin 119.
The adjustable pre-rotation nozzles 101 are uniformly arranged in the circumferential direction inside the cascade type pre-rotation channels 102, and the orientation of the adjustable pre-rotation nozzles 101 is radial and is used for pre-rotating two air flows entering the combustion chambers of the cascade type pre-rotation channels 102 so as to reduce the relative total temperature of cooling air.
The adjustable pre-rotation nozzle 101 comprises an adjustable pre-rotation nozzle guide vane 101a and a guide plate 101b, wherein the adjustable pre-rotation nozzle guide vane 101a can deflect at an angle relative to the guide plate 101b, the cross-sectional area of the adjustable pre-rotation nozzle 101 in the radial cross section of the cascade pre-rotation channel 102 is changed, the radial cross-sectional area of the cascade pre-rotation channel 102 is further increased or decreased, and the gas flow passing through the cascade pre-rotation channel 102 is adjusted.
The adjustable pre-rotation nozzle vane 101a is mounted on a fixed shaft 117 and is rotatable about the fixed shaft 117 during operation.
The maximum deflection angle of the pre-rotation nozzle guide vane 101a relative to the guide plate 101b corresponds to a sub-inspection state of the pre-rotation nozzle guide vane 101a, in which the pre-rotation nozzle guide vane 101a is partially overlapped with the guide plate 101b, the cross-sectional area of the adjustable pre-rotation nozzle 101 is maximum under the radial cross section of the cascade pre-rotation channel 102, and the gas flow through the cascade pre-rotation channel 102 is minimum; the minimum deflection angle of the turning pre-rotation nozzle guide vane 101a relative to the deflector 101b corresponds to the maximum state of the turning pre-rotation nozzle guide vane 101a, in which the turning pre-rotation nozzle guide vane 101a is fully overlapped with the deflector 101b, the cross-sectional area of the adjustable pre-rotation nozzle 101 at the radial cross-section of the cascade pre-rotation channel 102 is minimum, and the gas flow through the cascade pre-rotation channel 102 is maximum.
The drive mechanism is driven by an aircraft engine hydraulic system for driving deflection of the pre-rotation nozzle guide vane 101a relative to the deflector 101 b.
The hydraulic actuating mechanism 112, the actuating rod 113, the connecting rod 114, the actuating ring 115, the transmission rod 116 and the driving mechanism formed by the movement of the pin 119 are combined into 12 groups, and the outer sides of the pre-rotation channel support plates are uniformly arranged along the circumferential direction. One end of the hydraulic actuating mechanism 112 is fixed on the upper part of the combustion chamber outer ring 105 and is driven by an aero-engine hydraulic system; the other end of the hydraulic actuating mechanism 112 is connected with an actuating rod 113, and the actuating rod 113 can stretch and retract in the radial direction under the drive of the hydraulic actuating mechanism 112 so as to drive a connecting rod 114 to move; one end of the connecting rod 114 is connected with the actuating rod 113, and the other end is connected with the actuating ring 115; the actuating ring 115 is a thin-walled ring capable of rotating circumferentially under the action of the connecting rod 114; the actuating ring 115 is connected with the transmission rod 116 through a pin 119, drives the transmission rod 116 and the adjustable pre-rotation nozzle guide vane 101a connected with the transmission rod to rotate, and drives the adjustable pre-rotation nozzle guide vane 101a to deflect relative to the guide plate 101 b. FIG. 3 is a schematic diagram of an adjustable pre-rotation nozzle drive mechanism according to the present disclosure.
The cascade pre-swirl channel 102 is surrounded by a pre-swirl channel support plate for communicating the combustion chamber with the pre-swirl chamber 103.
The pre-swirl chamber 103 is used to collect pre-swirled cooling gas.
The cover 104 is used to form a cover cavity 111. The cover plate cavity 111 is a co-rotating cavity surrounded by the cover plate 104, the turbine disk 110 and the drum shaft 109 for storing and delivering turbine blade cooling gas; wherein the cover plate 104 overlaps the drum shaft 109. The cover plate 104 is provided with a receiving hole 104a, an outer sealing grate tooth 104b and an inner sealing grate tooth 104c; the receiving hole 104a is used for communicating the pre-rotation cavity 103 and the cover plate cavity 111.
The combustion chamber outer ring 105 is provided with a vent hole 105a, an outer grate seal ring 105b, an inner grate seal ring 105c, an orifice 105d, a pre-rotation channel outer support plate 105e and a pre-rotation channel inner support plate 105f; the vent hole 105a is used for communicating the unloading cavity 108 and the gas collecting cavity 106, so that rim sealing gas in the unloading cavity 108 can enter the gas collecting cavity 106; the outer grate seal ring 105b and the inner grate seal ring 105c are provided at the lower part of the combustion chamber outer ring 105.
The upper portion of the combustion chamber outer ring 105 extends downward to form a pre-swirl passage support plate. The pre-rotation channel struts and the combustion chamber outer ring 105 are secured to the engine stator support structure. The pre-rotation channel support plate comprises a pre-rotation channel outer support plate 105e and a pre-rotation channel inner support plate 105f, wherein the pre-rotation channel inner support plate 105f, the pre-rotation channel inner support plate 105f and the support plate 118 are of an integrated structure, and the pre-rotation channel inner support plate 105f is fixedly connected with the fixed rotating shaft 117.
During assembly, the adjustable pre-rotation nozzle guide vane 101a is firstly installed on the fixed rotating shaft 117, and then the pre-rotation channel outer support plate 105e and the pre-rotation channel inner support plate 105f are in butt joint.
The outer sealing grate teeth 104b, the inner sealing grate teeth 104c, the outer grate teeth sealing ring 105b, the inner grate teeth sealing ring 105c and the cover plate 104 jointly enclose to form a pre-rotation cavity 103; wherein the outer sealing grate teeth 104b are opposite to the outer grate teeth sealing ring 105b, and a gap is reserved between the outer sealing grate teeth 104b and the outer grate teeth sealing ring 105 b; the inner sealing comb teeth 104c are opposite to the inner comb teeth sealing ring 105c, and a gap is reserved between the inner sealing comb teeth 104c and the inner comb teeth sealing ring 105 c.
The outer grate teeth seal ring 105b and the pre-rotation channel outer support plate 105e are of an integrated structure, and the inner grate teeth seal ring 105c and the pre-rotation channel inner support plate 105f are of an integrated structure.
The turbine disk 110 is provided with an air supply hole 110a, and the air supply hole 110a is used for delivering cooling air in the cover plate cavity 111 to the turbine blades.
The two airflows of the combustion chamber pass through the cascade pre-rotation channels 102 to become pre-rotation cooling air, enter the pre-rotation cavity 103, enter the cover plate cavity 111 through the receiving holes 104a to become turbine blade cooling air, enter the turbine blades from the air supply holes 110a at the blade roots, and cool the turbine blades.
The rim seal gas is led out from the last stage of the high-pressure compressor, enters the gas collection cavity 106 through the vent hole 105a, and then enters the front disc seal cavity 107.
Specifically, when the air system of the aero-engine works, two airflows of the combustion chamber enter the cascade type pre-rotation channel 102 and deflect circumferentially, the relative total temperature of the airflows is reduced, and the airflows pass through the cascade type pre-rotation channel 102 and become pre-rotation cooling air to enter the pre-rotation cavity 103. The pre-rotation cavity 103 is formed by enclosing an outer sealing grate tooth 104b, an inner sealing grate tooth 104c, an outer grate tooth sealing ring 105b, an inner grate tooth sealing ring 105c and a cover plate 104; wherein, the outer sealing grate teeth 104b and the outer grate teeth sealing ring 105b act together to seal the pre-rotation cooling gas in the pre-rotation cavity 103 and isolate the pre-rotation cooling gas from the unloading cavity 108, and a gap exists between the outer sealing grate teeth 104b and the outer grate teeth sealing ring 105 b; the inner sealing grate teeth 104c and the inner grate teeth sealing ring 105c act together to seal the pre-spun cooling air in the pre-spinning cavity 103 from the front disc sealing cavity 107, and a gap exists between the inner sealing grate teeth 104c and the inner grate teeth sealing ring 105 c. The cover plate 104 is provided with a receiving hole 104a, and most of the pre-rotation cooling gas enters the cover plate cavity 111 through the receiving hole 104a except that a small part of the pre-rotation cooling gas leaks through a gap between the outer sealing comb teeth 104b and the outer comb teeth sealing ring 105b and a gap between the inner sealing comb teeth 104c and the inner comb teeth sealing ring 105 c. The cover plate cavity 111 is a co-rotating cavity surrounded by the cover plate 104, the turbine disk 110 and the drum shaft 109, and pre-rotation cooling air enters the cover plate cavity 111 to become turbine blade cooling air, and enters the turbine blades from the air supply holes 110a at the blade roots to cool the turbine blades.
The rim sealing gas enters the unloading cavity 108 from the last stage bleed air of the high-pressure compressor, and enters the gas collection cavity 106 through the vent hole 105 a; the air flow passes through the orifice 105d and is rim sealed after being mixed with pre-spun cooling air leaking through the inner sealing grate teeth 104c in the pre-disk sealing chamber 107. The leakage amount of pre-rotation cooling gas passing through the inner sealing grate teeth 104c is small, most of gas flow for rim sealing comes from rim sealing gas in the unloading cavity 108, the cooling flow path and the rim sealing flow path have small interaction, and fig. 4 is a schematic diagram of decoupling design of the blade cooling flow path and the rim sealing flow path.
36 groups of adjustable pre-spinning nozzles 101 are uniformly distributed in the inner circumference of the cascade type pre-spinning channel 102, each group of adjustable pre-spinning nozzles 101 comprises an adjustable pre-spinning nozzle guide vane 101a and a guide plate 101b, and fig. 2 is a schematic diagram of a partial enlarged structure of a plurality of groups of adjustable pre-spinning nozzles 101. Two different deflection angle states of the adjustable pre-rotation nozzle vane 101a are given in fig. 5, the maximum state and the sub-patrol state of the adjustable pre-rotation nozzle vane 101a, respectively. The adjustable pre-rotation nozzle guide vane 101a is attached to the guide plate 101b in the maximum state, and the vane back curve of the adjustable pre-rotation nozzle guide vane 101a and the tail curve of the guide plate 101b are in smooth transition. The leading edge curve of the deflector 101b is parallel to the leading edge curve of the adjustable pre-rotation nozzle vane 101 a. The deflection angle of the adjustable pre-rotation nozzle guide vane 101a is reduced, the cross-sectional area of the cascade type pre-rotation channel 102 is increased, the gas passing through the cascade type pre-rotation channel 102 is increased, and when the adjustable pre-rotation nozzle guide vane 101a is in a maximum state, the deflection angle of the adjustable pre-rotation nozzle guide vane 101a is reduced to the minimum and is attached to the guide plate 101 b; the deflection angle of the adjustable pre-rotation nozzle guide vane 101a increases, the cross-sectional area of the cascade type pre-rotation channel 102 decreases, and the gas passing through the cascade type pre-rotation channel 102 decreases due to the throttling effect of the adjustable pre-rotation nozzle guide vane 101a, and the deflection angle of the adjustable pre-rotation nozzle guide vane 101a increases to the maximum when the adjustable pre-rotation nozzle guide vane 101a is in the sub-patrol state.
According to the invention, according to different requirements of the cooling gas of the turbine blades in different flight states, the deflection angle of the adjustable pre-rotation nozzle guide vane 101a is adjusted, so that the adjustment of the air entraining proportion of the cooling gas can be realized. The conventional cover plate pre-rotation system of fig. 6 is geometrically non-adjustable, so that the bleed ratio of the turbine blade cooling gas at each flight condition is substantially unchanged. The radial adjustable pre-rotation system of the aero-engine blade grid disclosed by the invention increases the deflection angle of the adjustable pre-rotation nozzle guide vane by adjusting the deflection angle of the adjustable pre-rotation nozzle guide vane under the condition that the cooling gas demand of turbine blades such as take-off and climbing of an aircraft is large, and the air entraining proportion of the pre-rotation cooling gas is improved; the angle of the guide vane of the pre-spinning nozzle is reduced in the state that the cooling air demand of the turbine blades is small in the process of slow running, cruising, descending and the like of the aircraft, and the air entraining proportion of the pre-spinning cooling air is reduced, as shown in fig. 7.
The decoupling design of the rim seal flow path and the cooling flow path ensures the relative stability of the seal flow path flow when the pressure of the pre-rotation cavity 103 is changed in the process of adjusting the deflection angle of the adjustable pre-rotation nozzle guide vane. The conventional cover plate type pre-rotation system shown in fig. 6 directly causes the pressure difference at two ends of the external sealing comb teeth to be reduced due to the pressure change of the sealing cavity, and the flow of the sealing flow path is greatly reduced. Fig. 8 shows the influence of the pressure change of the pre-spinning cavities of two pre-spinning systems on the flow rate of a sealing flow path, and when the pressure of the pre-spinning cavities changes in the same amplitude, the variation of the sealing flow rate of the vane grid type radial adjustable pre-spinning system of the air system of the aero-engine disclosed by the invention is obviously smaller than that of a traditional cover plate type pre-spinning system.
Compared with the prior art, the vane grid type radial adjustable pre-rotation system of the aero-engine air system can change the throttling area of the adjustable pre-rotation nozzle guide vanes by adjusting the deflection angle of the adjustable pre-rotation nozzle guide vanes, so that the adjustment of the air-entraining amount of pre-rotation cooling air is realized, the hot end part of the engine is ensured to meet the requirement of allowable temperature by using cooling air with proper flow, meanwhile, the cooling air is saved as much as possible, the performance of the engine is ensured, and meanwhile, the events of endangering the engine, such as backflow of gas generated by a turbine blade air film Kong Yifa, are effectively avoided; the guide vane of the adjustable pre-rotation nozzle is attached to the guide vane in the maximum state, the vane back curve of the guide vane of the adjustable pre-rotation nozzle is in smooth transition with the tail curve of the guide vane, the front curve of the guide vane is concentric with the front curve of the guide vane of the adjustable pre-rotation nozzle, the air inlet angle is basically unchanged in the process of adjusting the deflection angle of the guide vane of the adjustable pre-rotation nozzle, thus the air inlet loss in the adjusting process is reduced, the air flow direction is relatively fixed when the angle adjustment is carried out on the adjustable pre-rotation nozzle through the combination of the guide vane and the guide vane of the adjustable pre-rotation nozzle, the flow loss in the cooling air flow adjusting process is reduced, and the efficient and stable adjustment of the cooling air flow is realized; because radial pre-rotation is adopted, the radius of the outlet of the adjustable pre-rotation nozzle is reduced, the radius of the sealing comb teeth positioned on two sides of the outlet of the adjustable pre-rotation nozzle is reduced, and the lower-radius comb teeth can adopt smaller sealing gaps, so that the leakage amount is reduced, the waste of pre-rotation gas is avoided, and meanwhile, the lower-position comb teeth gaps are less influenced by the deformation of a rotor stator, and the stability of an air system is improved; because of the existence of the sealing comb teeth at the two sides of the pre-rotation cavity, the pressure changes of the pre-rotation cavity, the disc front cavity and the unloading cavity are relatively independent, the great influence of the pressure changes of the pre-rotation cavity on the axial force during the angle adjustment of the adjustable pre-rotation nozzle is avoided, and the stability of an air system is further improved.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention.
Claims (10)
1. The cascade type radial adjustable pre-rotation system of the aero-engine air system is characterized by comprising an adjustable pre-rotation nozzle (101), a cascade type pre-rotation channel (102) and a driving mechanism; wherein,,
the adjustable pre-spinning nozzles (101) are uniformly arranged in the blade grid type pre-spinning channels (102) along the circumferential direction, and the direction of the adjustable pre-spinning nozzles (101) is radial and is used for pre-spinning cooling two air flows entering the combustion chambers of the blade grid type pre-spinning channels (102);
the adjustable pre-rotation nozzle (101) comprises an adjustable pre-rotation nozzle guide vane (101 a) and a guide plate (101 b), the adjustable pre-rotation nozzle guide vane (101 a) can deflect at an angle relative to the guide plate (101 b), the cross section area of the adjustable pre-rotation nozzle (101) in the radial cross section of the cascade pre-rotation channel (102) is changed, the radial cross section area of the cascade pre-rotation channel (102) is further increased or reduced, and the gas flow passing through the cascade pre-rotation channel (102) is adjusted;
the driving mechanism is driven by an aeroengine hydraulic system and is used for driving the adjustable pre-rotation nozzle guide vane (101 a) to deflect relative to the guide plate (101 b).
2. The cascade type radially adjustable pre-rotation system of an aeroengine air system according to claim 1, characterized in that the vane back curve of the adjustable pre-rotation nozzle vane (101 a) smoothly transitions with the tail curve of the deflector (101 b); the head curve of the deflector (101 b) is parallel to the front edge curve of the adjustable pre-rotation nozzle guide vane (101 a).
3. The cascade type radially adjustable pre-rotation system of an aeroengine air system according to claim 2, wherein the maximum deflection angle of the adjustable pre-rotation nozzle guide vane (101 a) with respect to the deflector (101 b) corresponds to a sub-patrol state of the adjustable pre-rotation nozzle guide vane (101 a), in which the adjustable pre-rotation nozzle guide vane (101 a) is partially overlapped with the deflector (101 b), the cross-sectional area of the adjustable pre-rotation nozzle (101) at the radial cross-section of the cascade type pre-rotation channel (102) is maximum, and the gas flow through the cascade type pre-rotation channel (102) is minimum; the minimum deflection angle of the adjustable pre-rotation nozzle guide vane (101 a) relative to the deflector (101 b) corresponds to the maximum state of the adjustable pre-rotation nozzle guide vane (101 a), in which the adjustable pre-rotation nozzle guide vane (101 a) is fully overlapped with the deflector (101 b), the cross-sectional area of the adjustable pre-rotation nozzle (101) is minimum under the radial cross section of the cascade pre-rotation channel (102), and the gas flow through the cascade pre-rotation channel (102) is maximum.
4. A cascade type radially adjustable pre-rotation system of an aero-engine air system according to claim 3, characterized in that the cascade type radially adjustable pre-rotation system of an aero-engine air system further comprises a combustion chamber outer ring (105) and a pre-rotation channel support plate; the upper part of the combustion chamber outer ring (105) extends downwards to form a pre-rotation channel support plate, and the pre-rotation channel support plate and the combustion chamber outer ring (105) are fixed on an engine stator supporting structure; the pre-rotation channel support plate surrounds and forms a blade grid type pre-rotation channel (102).
5. The cascade type radially adjustable pre-rotation system of an aeroengine air system according to claim 4, wherein the driving mechanism is uniformly arranged on the outer side of the pre-rotation channel support plate along the circumferential direction and comprises a hydraulic actuating mechanism (112), an actuating rod (113), a connecting rod (114), a transmission ring (115), a transmission rod (116) and a pin (119);
one end of a hydraulic actuating mechanism (112) is fixed on the upper part of the combustion chamber outer ring (105) and is driven by an aero-engine hydraulic system; the other end of the hydraulic actuating mechanism (112) is connected with an actuating rod (113), and the actuating rod (113) can stretch in the radial direction under the drive of the hydraulic actuating mechanism (112), so that a connecting rod (114) is driven to move; one end of the connecting rod (114) is connected with the actuating rod (113), and the other end is connected with the actuating ring (115); the actuating ring (115) is a thin-walled ring and can circumferentially rotate under the action of the connecting rod (114); the actuating ring (115) is connected with the transmission rod (116) through a pin (119) to drive the transmission rod (116) and the adjustable pre-rotation nozzle guide vane (101 a) connected with the transmission rod to rotate, and the adjustable pre-rotation nozzle guide vane (101 a) is driven to deflect relative to the guide plate (101 b).
6. The cascade radially adjustable pre-rotation system of an aircraft engine air system according to claim 5, characterized in that the cascade radially adjustable pre-rotation system of an aircraft engine air system further comprises a pre-rotation chamber (103) for collecting pre-rotated cooling gas through the cascade pre-rotation channel (102).
7. The cascade type radially adjustable pre-rotation system of an aero-engine air system according to claim 6, further comprising a cover plate (104), wherein the cover plate (104) is provided with outer sealing grate teeth (104 b) and inner sealing grate teeth (104 c); an outer grate tooth sealing ring (105 b) and an inner grate tooth sealing ring (105 c) are arranged at the lower part of the combustion chamber outer ring (105); the outer sealing grate teeth (104 b), the inner sealing grate teeth (104 c), the outer grate teeth sealing ring (105 b), the inner grate teeth sealing ring (105 c) and the cover plate (104) jointly surround to form a pre-rotation cavity (103).
8. The cascade radially adjustable pre-rotation system of an aero-engine air system according to claim 7, characterized in that the cascade radially adjustable pre-rotation system of an aero-engine air system further comprises an unloading chamber (108); the outer sealing comb teeth (104 b) and the outer comb teeth sealing ring (105 b) act together to seal the pre-rotation cooling gas in the pre-rotation cavity (103) and isolate the pre-rotation cooling gas from the unloading cavity (108).
9. The cascade radially adjustable pre-rotation system of an aero-engine air system according to claim 8, further comprising a pre-disk seal cavity (107); the inner sealing comb teeth (104 c) and the inner comb teeth sealing ring (105 c) jointly act to seal the pre-rotation cooling gas in the pre-rotation cavity (103) and isolate the pre-rotation cooling gas from the disc front sealing cavity (107).
10. The cascade radially adjustable pre-rotation system of an aeroengine air system according to claim 9, wherein a gap is present between the outer sealing grate teeth (104 b) and the outer grate teeth sealing ring (105 b); a gap exists between the inner sealing comb teeth (104 c) and the inner comb teeth sealing ring (105 c).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310928076.XA CN116906184A (en) | 2023-07-27 | 2023-07-27 | Cascade type radial adjustable pre-rotation system of aero-engine air system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310928076.XA CN116906184A (en) | 2023-07-27 | 2023-07-27 | Cascade type radial adjustable pre-rotation system of aero-engine air system |
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| Publication Number | Publication Date |
|---|---|
| CN116906184A true CN116906184A (en) | 2023-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310928076.XA Pending CN116906184A (en) | 2023-07-27 | 2023-07-27 | Cascade type radial adjustable pre-rotation system of aero-engine air system |
Country Status (1)
| Country | Link |
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| CN (1) | CN116906184A (en) |
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2023
- 2023-07-27 CN CN202310928076.XA patent/CN116906184A/en active Pending
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